Adaptive terminal sliding mode guidance law with impact angle constraint

被引：0
|
作者：
Yang S. [1 ]
Zhang K. [1 ]
Chen P. [1 ]
机构：
[1] Department of Missile Engineering, Ordnance Engineering College, Shijiazhuang
来源：
Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2016年 / 42卷 / 08期
关键词：
Exponential reaching law; Finite-time convergence; Guidance law; Impact angle constraint; Nonsingular terminal sliding mode control;
D O I：
10.13700/j.bh.1001-5965.2015.0502
中图分类号：
学科分类号：
摘要：
Aimed at the requirement of zero miss-distance and terminal impact angle constraint for some missiles attacking the targets, an adaptive nonsingular terminal sliding mode control algorithm based on the theories of terminal sliding mode control and finite-time control is proposed first. The algorithm avoids the singularity of terminal sliding mode control, and makes the state variables achieve the equilibrium point by improving a fast nonsingular terminal sliding mode function to construct the sliding mode surface, and employing an adaptive exponential reaching law. Then the algorithm is utilized to design the guidance law, and an adaptive nonsingular and finite-time convergent guidance law with impact angle constraint is proposed. Realizing the requirement of miss distance and attack angle of the missiles. Finite-time control theory is used to analyze the convergence of the guidance law, and proves the fast and finite-time convergence of guidance system states during the whole process. Compared with conventional nonsingular terminal sliding mode guidance law, the designed guidance law can attack the targets with less miss-distance and higher precision of expected impact angle in a shorter time. A large number of simulation experiments verify the validity of the proposed law. © 2016, Editorial Board of JBUAA. All right reserved.
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页码：1566 / 1574
页数：8
相关论文
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